Finite-difference procedures are used to solve axisymmetric thermal stress problems with aid of digital computer; elasticity theory is employed in stress-function formulation that includes effects of continuously varying temperatures in axial and radial directions; use of these techniques permits details such as curved boundaries and multimaterial assemblies to be incorporated into computer program; experimental test program was developed concurrently and solutions are compared with photoelastic model studies and with measurements made on complete propellant-grain systems; solutions to propellant-grain problems are presented.


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    Title :

    Transient thermal stresses in solid-propellant grains


    Additional title:

    J Spacecraft Rockets


    Contributors:

    Published in:

    Publication date :

    1965


    Size :

    6 pages


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English




    Transient thermal stresses in solid-propellant grains

    MESSNER, A. M. / SCHLIESSMANN, D. R. | AIAA | 1965


    Transient thermal stresses in solid propellant grains

    MESSNER, A. / SCHLIESSMANN, D. | AIAA | 1964



    Stresses owing to internal pressure in solid propellant rocket grains

    Wilson, Jr., H.B. | Engineering Index Backfile | 1961


    Structural assessment of solid propellant grains

    NATO, Propulsion and Energetics Panel | TIBKAT | 1997